A large-thickness high-temperature protective coating on the inner wall of a turbine outer ring and its preparation method

A technology of protective coating and large thickness, which is applied in the direction of coating, metal material coating process, fusion spraying, etc. It can solve the problems of abnormal blade tip scraping, high temperature corrosive medium erosion, long-term vibration, etc., and achieve noise reduction And the effect of heat pollution control, enhanced cohesive strength, and small velocity gradient

Active Publication Date: 2020-10-16
GUANGDONG INST OF NEW MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, as the thickness of the coating increases, the internal residual stress is more likely to concentrate, and there are problems such as long-term vibration, abnormal scraping of the blade tip, and erosion of high-temperature corrosive media during service, resulting in the coating on the inner wall of the outer ring of the turbine. The coating is prone to partial or overall peeling off

Method used

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  • A large-thickness high-temperature protective coating on the inner wall of a turbine outer ring and its preparation method
  • A large-thickness high-temperature protective coating on the inner wall of a turbine outer ring and its preparation method
  • A large-thickness high-temperature protective coating on the inner wall of a turbine outer ring and its preparation method

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preparation example Construction

[0023] An embodiment of the present invention provides a method for preparing the above-mentioned large-thickness high-temperature protective coating on the inner wall of the outer ring of the turbine, including:

[0024] The inner wall of the pretreated turbine outer ring is sprayed at least twice, and the coating is subjected to stress relief heat treatment and secondary sandblasting between two adjacent sprayings. After the spraying is completed, the coating is subjected to vacuum diffusion heat treatment.

[0025] Specifically, after the outer ring of the superalloy turbine is degreased and degreased, the position to be sprayed is pretreated. The pretreatment in the embodiment of the present invention includes sandblasting, transferred arc cleaning and preheating.

[0026] Sandblasting can remove the oxide skin on the surface of the turbine outer ring to be sprayed to increase surface activity and improve the bonding strength between the coating and the turbine outer ring....

Embodiment 1

[0041] This embodiment provides a large-thickness high-temperature protective coating on the inner wall of the outer ring of the turbine, which is mainly produced through the following steps:

[0042] (1) Degrease and degrease the outer ring of the GH3536 superalloy turbine. The sprayed surface is roughened by sandblasting with zirconium corundum. The sand grain size is 24#, the sandblasting pressure is 0.45MPa, and the sandblasting distance is 200mm. sand or dust.

[0043] (2) Put the sandblasted and roughened turbine outer ring into the fixture and place it in a low-pressure plasma spraying vacuum chamber, evacuate to 0.5mbar, then backfill with argon to 40mbar, and perform transferred arc cleaning on the turbine outer ring, plasma The spray gun current is 600A, the transferred arc current is 25A, the argon gas is 60L / min, the hydrogen gas is 2L / min, the spray distance is 300mm, the spray gun moving speed is 500mm / s, and the turbine outer ring speed is 60rpm.

[0044] (3) P...

Embodiment 2

[0051] This embodiment provides a large-thickness high-temperature protective coating on the inner wall of the outer ring of the turbine, which is mainly produced through the following steps:

[0052] (1) Degrease and degrease the outer ring of the GH4648 superalloy turbine. The sprayed surface is roughened by sandblasting with brown corundum. The sand size is 30#, the sandblasting pressure is 0.40MPa, and the sandblasting distance is 160mm. sand or dust.

[0053] (2) Put the sand blasted roughened turbine outer ring into the fixture and place it in a low-pressure plasma spraying vacuum chamber, evacuate to 0.5mbar, then backfill with argon to 35mbar, and perform transferred arc cleaning on the turbine outer ring, plasma The spray gun current is 580A, the transferred arc current is 28A, the argon gas is 62L / min, the hydrogen gas is 1L / min, the spray distance is 320mm, the spray gun moving speed is 450mm / s, and the turbine outer ring speed is 50rpm.

[0054] (3) Preheat treatm...

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Abstract

The invention relates to a high-thickness high-temperature protection coating for the inner wall of a turbine outer ring and a preparation method of the coating and belongs to the technical field of material surface processing. The high-thickness high-temperature protection coating includes a high-temperature alloy turbine outer ring and a coating body arranged on the inner wall of the turbine outer ring,and the coating body is made of CoNiCrAlY. The coating is uniform and compact in structure,appropriate in hardness and excellent in high-temperature protection performance. The preparation method of the high-thickness high-temperature protection coating for the inner wall of the turbine outer ring includes the steps of conducting spraying on the inner wall of the pretreated turbine outer ring at least twice,conducting destress thermal treatment and secondary sand blasting treatment on the coating body at the interval of two continuous times of spraying,and conducting vacuum heat dissipation treatment on the coating body after spraying is completed. The preparation method enhances the combination strength of the coating body and the turbine outer ring and the cohesion strength of the coating body and can significantly reduce the shedding risk of the high-thickness coating and increase the yield of the coating.

Description

technical field [0001] The invention relates to the technical field of material surface treatment, and in particular to a large-thickness high-temperature protective coating on the inner wall of a turbine outer ring and a preparation method thereof. Background technique [0002] As the "heart" of an aircraft, an aero-engine can provide the aircraft with the power required for flight. It is a highly complex and sophisticated thermodynamic mechanism, and its core components include air compressors, combustion chambers, and turbines. Wherein, the turbine includes a turbine outer ring and turbine rotor blades, the rotor blades are arranged in the ring of the turbine outer ring, and the tip of the blade faces the inner wall of the turbine outer ring. As an important part of the gas flow path of the engine, the outer ring of the turbine mainly plays the role of controlling the tip clearance of the turbine during the working state. According to reports, 1 / 3 of the turbine performa...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C23C4/134C23C4/073C23C4/18C23C4/02
CPCC23C4/02C23C4/073C23C4/134C23C4/18
Inventor 杨焜刘敏牛少鹏邓子谦曾威陈龙飞宋进兵邓春明邓畅光代明江周克崧
Owner GUANGDONG INST OF NEW MATERIALS
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